EP3063385A4 - Getriebeturbolüfteranordnung mit geteilter kernleistung - Google Patents

Getriebeturbolüfteranordnung mit geteilter kernleistung Download PDF

Info

Publication number
EP3063385A4
EP3063385A4 EP14880285.3A EP14880285A EP3063385A4 EP 3063385 A4 EP3063385 A4 EP 3063385A4 EP 14880285 A EP14880285 A EP 14880285A EP 3063385 A4 EP3063385 A4 EP 3063385A4
Authority
EP
European Patent Office
Prior art keywords
power ratio
split power
geared turbofan
core split
turbofan arrangement
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
EP14880285.3A
Other languages
English (en)
French (fr)
Other versions
EP3063385A2 (de
Inventor
Daniel Bernard KUPRATIS
Frederick M. Schwarz
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
RTX Corp
Original Assignee
United Technologies Corp
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Priority claimed from US14/177,372 external-priority patent/US10267228B2/en
Application filed by United Technologies Corp filed Critical United Technologies Corp
Publication of EP3063385A2 publication Critical patent/EP3063385A2/de
Publication of EP3063385A4 publication Critical patent/EP3063385A4/de
Pending legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/107—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with two or more rotors connected by power transmission
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/187—Convection cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/36—Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/06—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front fan
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/40—Transmission of power
    • F05D2260/403—Transmission of power through the shape of the drive components
    • F05D2260/4031—Transmission of power through the shape of the drive components as in toothed gearing
    • F05D2260/40311—Transmission of power through the shape of the drive components as in toothed gearing of the epicyclical, planetary or differential type
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/40—Organic materials
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/606—Directionally-solidified crystalline structures
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP14880285.3A 2013-11-01 2014-10-29 Getriebeturbolüfteranordnung mit geteilter kernleistung Pending EP3063385A4 (de)

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
US201361898731P 2013-11-01 2013-11-01
US201361899464P 2013-11-04 2013-11-04
US14/177,372 US10267228B2 (en) 2013-10-31 2014-02-11 Geared turbofan arrangement with core split power ratio
PCT/US2014/062764 WO2015112212A2 (en) 2013-11-01 2014-10-29 Geared turbofan arrangement with core split power ratio

Publications (2)

Publication Number Publication Date
EP3063385A2 EP3063385A2 (de) 2016-09-07
EP3063385A4 true EP3063385A4 (de) 2017-07-12

Family

ID=53682087

Family Applications (1)

Application Number Title Priority Date Filing Date
EP14880285.3A Pending EP3063385A4 (de) 2013-11-01 2014-10-29 Getriebeturbolüfteranordnung mit geteilter kernleistung

Country Status (3)

Country Link
US (2) US11125155B2 (de)
EP (1) EP3063385A4 (de)
WO (1) WO2015112212A2 (de)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3063385A4 (de) * 2013-11-01 2017-07-12 United Technologies Corporation Getriebeturbolüfteranordnung mit geteilter kernleistung
US10502163B2 (en) * 2013-11-01 2019-12-10 United Technologies Corporation Geared turbofan arrangement with core split power ratio
FR3093768B1 (fr) * 2019-03-13 2021-07-02 Safran Aircraft Engines Procédé et système de surveillance d’un état d’un réducteur d’une turbine à gaz

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4251987A (en) * 1979-08-22 1981-02-24 General Electric Company Differential geared engine
US4827712A (en) * 1986-12-23 1989-05-09 Rolls-Royce Plc Turbofan gas turbine engine
US20070012026A1 (en) * 2000-09-05 2007-01-18 Dev Sudarshan P Nested core gas turbine engine
US20130259653A1 (en) * 2012-04-02 2013-10-03 Frederick M. Schwarz Geared turbofan engine with power density range
US20130287545A1 (en) * 2012-04-25 2013-10-31 Gabriel L. Suciu Geared turbofan with three turbines all counter-rotating

Family Cites Families (102)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2258792A (en) 1941-04-12 1941-10-14 Westinghouse Electric & Mfg Co Turbine blading
US3021731A (en) 1951-11-10 1962-02-20 Wilhelm G Stoeckicht Planetary gear transmission
US2936655A (en) 1955-11-04 1960-05-17 Gen Motors Corp Self-aligning planetary gearing
US3194487A (en) 1963-06-04 1965-07-13 United Aircraft Corp Noise abatement method and apparatus
US3287906A (en) 1965-07-20 1966-11-29 Gen Motors Corp Cooled gas turbine vanes
US3352178A (en) 1965-11-15 1967-11-14 Gen Motors Corp Planetary gearing
US3412560A (en) 1966-08-03 1968-11-26 Gen Motors Corp Jet propulsion engine with cooled combustion chamber, fuel heater, and induced air-flow
US3664612A (en) 1969-12-22 1972-05-23 Boeing Co Aircraft engine variable highlight inlet
GB1350431A (en) 1971-01-08 1974-04-18 Secr Defence Gearing
US3892358A (en) 1971-03-17 1975-07-01 Gen Electric Nozzle seal
US3765623A (en) 1971-10-04 1973-10-16 Mc Donnell Douglas Corp Air inlet
US3747343A (en) 1972-02-10 1973-07-24 United Aircraft Corp Low noise prop-fan
GB1418905A (en) 1972-05-09 1975-12-24 Rolls Royce Gas turbine engines
US3843277A (en) 1973-02-14 1974-10-22 Gen Electric Sound attenuating inlet duct
US3988889A (en) 1974-02-25 1976-11-02 General Electric Company Cowling arrangement for a turbofan engine
US3932058A (en) 1974-06-07 1976-01-13 United Technologies Corporation Control system for variable pitch fan propulsor
US3935558A (en) 1974-12-11 1976-01-27 United Technologies Corporation Surge detector for turbine engines
US4130872A (en) 1975-10-10 1978-12-19 The United States Of America As Represented By The Secretary Of The Air Force Method and system of controlling a jet engine for avoiding engine surge
GB1516041A (en) 1977-02-14 1978-06-28 Secr Defence Multistage axial flow compressor stators
US4240250A (en) 1977-12-27 1980-12-23 The Boeing Company Noise reducing air inlet for gas turbine engines
GB2041090A (en) 1979-01-31 1980-09-03 Rolls Royce By-pass gas turbine engines
US4284174A (en) 1979-04-18 1981-08-18 Avco Corporation Emergency oil/mist system
US4220171A (en) 1979-05-14 1980-09-02 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Curved centerline air intake for a gas turbine engine
US4289360A (en) 1979-08-23 1981-09-15 General Electric Company Bearing damper system
DE2940446C2 (de) 1979-10-05 1982-07-08 B. Braun Melsungen Ag, 3508 Melsungen Züchtung von tierischen Zellen in Suspensions- und Monolayerkulturen in Fermentationsgefäßen
US4478551A (en) 1981-12-08 1984-10-23 United Technologies Corporation Turbine exhaust case design
US5079916A (en) 1982-11-01 1992-01-14 General Electric Company Counter rotation power turbine
US4722357A (en) 1986-04-11 1988-02-02 United Technologies Corporation Gas turbine engine nacelle
US4696156A (en) 1986-06-03 1987-09-29 United Technologies Corporation Fuel and oil heat management system for a gas turbine engine
US4782658A (en) 1987-05-07 1988-11-08 Rolls-Royce Plc Deicing of a geared gas turbine engine
US4916894A (en) 1989-01-03 1990-04-17 General Electric Company High bypass turbofan engine having a partially geared fan drive turbine
US4979362A (en) 1989-05-17 1990-12-25 Sundstrand Corporation Aircraft engine starting and emergency power generating system
US5058617A (en) 1990-07-23 1991-10-22 General Electric Company Nacelle inlet for an aircraft gas turbine engine
US5141400A (en) 1991-01-25 1992-08-25 General Electric Company Wide chord fan blade
US5102379A (en) 1991-03-25 1992-04-07 United Technologies Corporation Journal bearing arrangement
US5317877A (en) 1992-08-03 1994-06-07 General Electric Company Intercooled turbine blade cooling air feed system
US5447411A (en) 1993-06-10 1995-09-05 Martin Marietta Corporation Light weight fan blade containment system
US5466198A (en) 1993-06-11 1995-11-14 United Technologies Corporation Geared drive system for a bladed propulsor
US5361580A (en) 1993-06-18 1994-11-08 General Electric Company Gas turbine engine rotor support system
US5524847A (en) 1993-09-07 1996-06-11 United Technologies Corporation Nacelle and mounting arrangement for an aircraft engine
RU2082824C1 (ru) 1994-03-10 1997-06-27 Московский государственный авиационный институт (технический университет) Способ защиты жаропрочных материалов от воздействия агрессивных сред высокоскоростных газовых потоков (варианты)
US5433674A (en) 1994-04-12 1995-07-18 United Technologies Corporation Coupling system for a planetary gear train
US5778659A (en) 1994-10-20 1998-07-14 United Technologies Corporation Variable area fan exhaust nozzle having mechanically separate sleeve and thrust reverser actuation systems
EP0839285B1 (de) 1994-12-14 2001-07-18 United Technologies Corporation Druckkontrolle eines verdichters mittels messung eines asymetrischen luftstroms
JP2969075B2 (ja) 1996-02-26 1999-11-02 ジャパンゴアテックス株式会社 脱気装置
US5809772A (en) 1996-03-29 1998-09-22 General Electric Company Turbofan engine with a core driven supercharged bypass duct
US5634767A (en) 1996-03-29 1997-06-03 General Electric Company Turbine frame having spindle mounted liner
US5857836A (en) 1996-09-10 1999-01-12 Aerodyne Research, Inc. Evaporatively cooled rotor for a gas turbine engine
US5975841A (en) 1997-10-03 1999-11-02 Thermal Corp. Heat pipe cooling for turbine stators
US5985470A (en) 1998-03-16 1999-11-16 General Electric Company Thermal/environmental barrier coating system for silicon-based materials
US6517341B1 (en) 1999-02-26 2003-02-11 General Electric Company Method to prevent recession loss of silica and silicon-containing materials in combustion gas environments
US6410148B1 (en) 1999-04-15 2002-06-25 General Electric Co. Silicon based substrate with environmental/ thermal barrier layer
US6315815B1 (en) 1999-12-16 2001-11-13 United Technologies Corporation Membrane based fuel deoxygenator
US6223616B1 (en) 1999-12-22 2001-05-01 United Technologies Corporation Star gear system with lubrication circuit and lubrication method therefor
US6318070B1 (en) 2000-03-03 2001-11-20 United Technologies Corporation Variable area nozzle for gas turbine engines driven by shape memory alloy actuators
US6444335B1 (en) 2000-04-06 2002-09-03 General Electric Company Thermal/environmental barrier coating for silicon-containing materials
US6708482B2 (en) 2001-11-29 2004-03-23 General Electric Company Aircraft engine with inter-turbine engine frame
US6607165B1 (en) 2002-06-28 2003-08-19 General Electric Company Aircraft engine mount with single thrust link
US6814541B2 (en) 2002-10-07 2004-11-09 General Electric Company Jet aircraft fan case containment design
US7021042B2 (en) 2002-12-13 2006-04-04 United Technologies Corporation Geartrain coupling for a turbofan engine
US6709492B1 (en) 2003-04-04 2004-03-23 United Technologies Corporation Planar membrane deoxygenator
US6895741B2 (en) 2003-06-23 2005-05-24 Pratt & Whitney Canada Corp. Differential geared turbine engine with torque modulation capability
GB0406174D0 (en) * 2004-03-19 2004-04-21 Rolls Royce Plc Turbine engine arrangement
DE102004016246A1 (de) 2004-04-02 2005-10-20 Mtu Aero Engines Gmbh Turbine, insbesondere Niederdruckturbine, einer Gasturbine, insbesondere eines Flugtriebwerks
US7328580B2 (en) 2004-06-23 2008-02-12 General Electric Company Chevron film cooled wall
US7937927B2 (en) 2004-12-01 2011-05-10 United Technologies Corporation Counter-rotating gearbox for tip turbine engine
GB0506685D0 (en) 2005-04-01 2005-05-11 Hopkins David R A design to increase and smoothly improve the throughput of fluid (air or gas) through the inlet fan (or fans) of an aero-engine system
US7374403B2 (en) 2005-04-07 2008-05-20 General Electric Company Low solidity turbofan
WO2007038674A1 (en) 2005-09-28 2007-04-05 Entrotech Composites, Llc Braid-reinforced composites and processes for their preparation
US7591754B2 (en) 2006-03-22 2009-09-22 United Technologies Corporation Epicyclic gear train integral sun gear coupling design
BE1017135A3 (nl) 2006-05-11 2008-03-04 Hansen Transmissions Int Een tandwielkast voor een windturbine.
US20080003096A1 (en) 2006-06-29 2008-01-03 United Technologies Corporation High coverage cooling hole shape
JP4911344B2 (ja) 2006-07-04 2012-04-04 株式会社Ｉｈｉ ターボファンエンジン
US8585538B2 (en) 2006-07-05 2013-11-19 United Technologies Corporation Coupling system for a star gear train in a gas turbine engine
US7926260B2 (en) 2006-07-05 2011-04-19 United Technologies Corporation Flexible shaft for gas turbine engine
EP3128164B1 (de) 2006-08-22 2019-07-10 Rolls-Royce North American Technologies, Inc. Gasturbinenmotor mit zwischengeschwindigkeitsverstärker
US7632064B2 (en) 2006-09-01 2009-12-15 United Technologies Corporation Variable geometry guide vane for a gas turbine engine
WO2008045072A1 (en) 2006-10-12 2008-04-17 United Technologies Corporation Dual function cascade integrated variable area fan nozzle and thrust reverser
US7662059B2 (en) 2006-10-18 2010-02-16 United Technologies Corporation Lubrication of windmilling journal bearings
US8020665B2 (en) 2006-11-22 2011-09-20 United Technologies Corporation Lubrication system with extended emergency operability
US7791235B2 (en) 2006-12-22 2010-09-07 General Electric Company Variable magnetic coupling of rotating machinery
US8017188B2 (en) 2007-04-17 2011-09-13 General Electric Company Methods of making articles having toughened and untoughened regions
US7950237B2 (en) 2007-06-25 2011-05-31 United Technologies Corporation Managing spool bearing load using variable area flow nozzle
US20120124964A1 (en) 2007-07-27 2012-05-24 Hasel Karl L Gas turbine engine with improved fuel efficiency
US8256707B2 (en) 2007-08-01 2012-09-04 United Technologies Corporation Engine mounting configuration for a turbofan gas turbine engine
US8075261B2 (en) 2007-09-21 2011-12-13 United Technologies Corporation Gas turbine engine compressor case mounting arrangement
US8205432B2 (en) 2007-10-03 2012-06-26 United Technologies Corporation Epicyclic gear train for turbo fan engine
US8128021B2 (en) 2008-06-02 2012-03-06 United Technologies Corporation Engine mount system for a turbofan gas turbine engine
US8099944B2 (en) 2008-10-08 2012-01-24 The Invention Science Fund I, Llc Hybrid propulsive engine including at least one independently rotatable propeller/fan
US7997868B1 (en) 2008-11-18 2011-08-16 Florida Turbine Technologies, Inc. Film cooling hole for turbine airfoil
US8307626B2 (en) 2009-02-26 2012-11-13 United Technologies Corporation Auxiliary pump system for fan drive gear system
US8181441B2 (en) 2009-02-27 2012-05-22 United Technologies Corporation Controlled fan stream flow bypass
GB0903423D0 (en) 2009-03-02 2009-04-08 Rolls Royce Plc Variable drive gas turbine engine
US8172716B2 (en) 2009-06-25 2012-05-08 United Technologies Corporation Epicyclic gear system with superfinished journal bearing
US8176725B2 (en) 2009-09-09 2012-05-15 United Technologies Corporation Reversed-flow core for a turbofan with a fan drive gear system
GB2474286B (en) 2009-10-12 2011-08-31 Rolls Royce Plc A propulsion engine
US9170616B2 (en) 2009-12-31 2015-10-27 Intel Corporation Quiet system cooling using coupled optimization between integrated micro porous absorbers and rotors
US8905713B2 (en) 2010-05-28 2014-12-09 General Electric Company Articles which include chevron film cooling holes, and related processes
US8257024B1 (en) 2012-01-27 2012-09-04 United Technologies Corporation Geared turbomachine fluid delivery system
US10267228B2 (en) * 2013-10-31 2019-04-23 United Technologies Corporation Geared turbofan arrangement with core split power ratio
EP3063385A4 (de) * 2013-11-01 2017-07-12 United Technologies Corporation Getriebeturbolüfteranordnung mit geteilter kernleistung
US10502163B2 (en) * 2013-11-01 2019-12-10 United Technologies Corporation Geared turbofan arrangement with core split power ratio

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4251987A (en) * 1979-08-22 1981-02-24 General Electric Company Differential geared engine
US4827712A (en) * 1986-12-23 1989-05-09 Rolls-Royce Plc Turbofan gas turbine engine
US20070012026A1 (en) * 2000-09-05 2007-01-18 Dev Sudarshan P Nested core gas turbine engine
US20130259653A1 (en) * 2012-04-02 2013-10-03 Frederick M. Schwarz Geared turbofan engine with power density range
US20130287545A1 (en) * 2012-04-25 2013-10-31 Gabriel L. Suciu Geared turbofan with three turbines all counter-rotating

Also Published As

Publication number Publication date
EP3063385A2 (de) 2016-09-07
US20200025069A1 (en) 2020-01-23
US20210355866A1 (en) 2021-11-18
US11578651B2 (en) 2023-02-14
US11125155B2 (en) 2021-09-21
WO2015112212A3 (en) 2015-10-29
WO2015112212A2 (en) 2015-07-30

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